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公开(公告)号：US20160244155A1
公开(公告)日：2016-08-25
申请号：US14626365
申请日：2015-02-19
发明人： William A. Amante
CPC分类号： B64C25/52 , B64C2025/325
摘要： A landing gear for an aircraft can include a skid tube having an inboard flat side wall and an outboard flat side wall, the skid tube having a skid tube centerline plane that is parallel to at least one of the outboard flat side wall and the inboard flat side wall, the skid tube being canted inboard at an angle The landing gear can include a forward cross tube having a straight horizontal portion, a first bend transitioning the straight horizontal portion into a straight angled portion, and a second bend transitioning the straight angled portion into a straight end portion.
摘要翻译： 用于飞机的起落架可以包括具有内侧平坦侧壁和外侧平坦侧壁的滑动管，所述滑动管具有平滑于所述外侧平坦侧壁和内侧平面中的至少一个的滑动管中心线平面 侧壁，滑动管以一定角度倾斜在内侧。起落架可包括具有直的水平部分的前横梁，第一弯曲部将直的水平部分转变成直角部分，以及将直角部分 进入直的端部。
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公开(公告)号：US09346538B2
公开(公告)日：2016-05-24
申请号：US14377018
申请日：2013-01-23
发明人： Yann Simonneaux , Simon D. Harris
CPC分类号： B64C25/16 , B64C25/32 , B64C2025/003
摘要： An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.
摘要翻译： 一种包括轮和整流罩的飞行器起落架，其布置成可在第一和第二构造之间移动，其中在第一构造中，整流罩布置成将起落架的元件与入射气流屏蔽，并且其中在第二构造中， 布置成偏转碎片或从一个或多个轮子推进的喷雾。
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公开(公告)号：US20160075447A1
公开(公告)日：2016-03-17
申请号：US14948220
申请日：2015-11-20
发明人： Mingyu Wang
CPC分类号： B64D25/00 , B64C25/32 , B64C25/54 , B64C25/56 , B64C39/024 , B64C2201/027 , B64D45/00 , B64D2201/00
摘要： An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.
摘要翻译： 提供了一种冲击保护装置，包括构造成保持压缩气体的气体容器和构造成由气体膨胀并充当诸如飞行器的可移动物体的气囊的充气构件。 响应于来自阀控制器的信号，阀控制气体从容器到可膨胀构件的流动。 阀和阀门控制器由与可移动物体的一个或多个其它系统相独立的电源供电。 还可以提供一种安全机构，除非被去激活，否则防止可膨胀构件的膨胀。
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公开(公告)号：US09254912B2
公开(公告)日：2016-02-09
申请号：US14237598
申请日：2012-08-20
申请人： Dominique Ducos
发明人： Dominique Ducos
CPC分类号： B64C25/001 , B64C25/32
摘要： An anti-lofting deflector for landing gear having two wheels on an axle. The deflector comprises a stationary support (5) for being fastened in service to a portion of the landing gear that carries the axle in order to extend between the wheels and present a distal end behind the wheels. It also has a first flap (2) hinged to the support via its distal end about a first hinge axis (X1) substantially parallel to the axle and a second flap (3) hinged to the first flap about a second hinge axis (X2) substantially parallel to the first hinge axis. Finally, there is a a return member (11) arranged so as to urge the second flap against an abutment of the first flap that prevents the second flap from becoming aligned with the first flap, and to urge the first flap against an abutment of the stationary support that prevents the first flap from folding against the support.
摘要翻译： 一种用于起落架的防抱板偏转器，在轴上具有两个轮子。 偏转器包括固定支撑件（5），用于固定在起落架的一部分上，所述起落架承载车轴，以便在车轮之间延伸并且在车轮之后提供远端。 它还具有围绕基本上平行于车轴的第一铰链轴线（X1）经由其远端铰接到支撑件的第一挡板（2），以及围绕第二铰链轴线（X2）铰接到第一挡板的第二挡板（3） 基本上平行于第一铰链轴线。 最后，设置有一个返回构件（11），以便将第二挡板推压抵靠第一挡板的邻接部分，从而防止第二挡片与第一挡片对准，并且将第一挡板推靠在固定件 支撑件防止第一挡板折叠支撑。
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公开(公告)号：US09162758B2
公开(公告)日：2015-10-20
申请号：US14534127
申请日：2014-11-05
发明人： Tao Wang , Tao Zhao , Shaojie Chen , Zhigang Ou
摘要： The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
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公开(公告)号：US09067675B2
公开(公告)日：2015-06-30
申请号：US13736632
申请日：2013-01-08
申请人： The Boeing Company
摘要： A system, an apparatus, and a method for an aerospace vehicle braking system for decelerating an aerospace vehicle on a landing surface. An arm is provided having a first portion connected to the aerospace vehicle and a second portion generally distal to the first portion. The second portion of the arm includes an engagement portion configured to engage the landing surface. The arm is movable between a first position, wherein the engagement portion is substantially disengaged from the landing surface, and a second position, wherein the engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. The engagement portion is configured to pivot with respect to the arm in response to the direction of travel of the aerospace vehicle upon the landing surface. An actuator is connected to the arm to selectively move the arm between the first position and the second position.
摘要翻译： 一种用于航空航天车辆制动系统的系统，装置和方法，用于使航空航天器在着陆面上减速。 臂被设置有具有连接到航空航天车辆的第一部分和大致远离第一部分的第二部分。 臂的第二部分包括被配置为接合着陆表面的接合部分。 臂可在第一位置和第二位置之间移动，第一位置与接合部分基本上脱离接合表面;第二位置，其中接合部分以足以使航空航天车辆显着减速的力与着陆面接合。 接合部分构造成响应于航空航天器在着陆表面上的行进方向相对于臂枢转。 致动器连接到臂以选择性地在第一位置和第二位置之间移动臂。
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57.发明授权Landing gear vibration absorber and method of operating said landing gear vibration absorber 有权起落架减振器和操作所述起落架减振器的方法公开(公告)号：US08967536B2
公开(公告)日：2015-03-03
申请号：US13716460
申请日：2012-12-17
发明人： Raphael Rammer , Peter Znika
CPC分类号： B64C27/001 , B64C2025/325 , B64C2027/005 , F16F7/116 , Y10T29/49764
摘要： A landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring-mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).
摘要翻译： 具有起落架（3）的直升机（2）的起落架减震器（1）包括一对滑板（4,5）和至少一个用于安装滑行件（4,5）的横管（6,7） ）到直升机的机身（8）。 至少一个弹簧质量系统（10,20,24）安装到起落架（3）。 所述至少一个弹簧 - 质量系统（10,20,24）被调谐到所述直升机的主激励频率，并且所述至少一个弹簧质量系统（10,20,24）位于或接近所述直升机的至少一个波腹 起落架（3）。 本发明还涉及一种操作直升机（2）的起落架减震器（1）的方法。
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公开(公告)号：US08899518B2
公开(公告)日：2014-12-02
申请号：US13127616
申请日：2008-11-11
申请人： Chris Foster , Ching Yu Hui
发明人： Chris Foster , Ching Yu Hui
CPC分类号： B64C25/32
摘要： An engine debris guard for preventing tyre propelled debris striking an aircraft engine, the debris guard comprising a guard bar pivotably connected to an aircraft main landing gear having at least one wheel and tyre assembly, the guard bar being arranged to be movable between a first position and a second position wherein in the first position the guard bar extends laterally across the wheel and tyre assembly to intersect the possible trajectories between the wheel and tyre assembly and an engine of the aircraft of any tyre propelled debris.
摘要翻译： 一种用于防止轮胎推进碎片撞击飞机发动机的发动机碎片防护件，所述碎片防护件包括可枢转地连接到具有至少一个轮和轮胎组件的飞机主起落架的防护杆，所述防护杆布置成可在第一位置 以及第二位置，其中在第一位置，护杆横向延伸穿过车轮和轮胎组件以与车轮和轮胎组件之间的可能的轨迹和任何轮胎推进碎片的飞行器的发动机相交。
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公开(公告)号：US08794566B2
公开(公告)日：2014-08-05
申请号：US13565654
申请日：2012-08-02
申请人： Donald B. Hutson
发明人： Donald B. Hutson
CPC分类号： B64D47/08 , B64C27/006 , B64C27/10 , B64C27/20 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/042 , B64C2201/066 , B64C2201/108 , B64C2201/121 , B64C2201/126 , B64C2201/127 , B64C2201/182 , B64D9/00 , F16M11/123 , F16M11/18 , F16M13/00 , F16M13/02 , F16M2200/041
摘要： In specific embodiments, a vehicle propellable through fluids comprises a main work section and a plurality of propulsion units. The main work section includes a payload support hub, a payload support structure rotatable in 360° about the payload support hub in at least one axis, and a core including at least one microprocessor, the core at least partially nested within the payload support hub. The at least one microprocessor is adapted to substantially maintain an orientation of the payload support structure relative to a horizon line as the vehicle is propelled. One or more payloads are mountable on the rotatable payload support structure.
摘要翻译： 在具体实施例中，通过流体推进的车辆包括主工作部分和多个推进单元。 主工作部分包括有效载荷支撑轮毂，在至少一个轴线上围绕有效载荷支撑轮毂360°旋转的有效载荷支撑结构，以及包括至少一个微处理器的核心，至少部分地嵌套在有效载荷支撑轮毂内。 所述至少一个微处理器适于在车辆被推进时基本上保持有效载荷支撑结构相对于水平线的取向。 一个或多个有效载荷可安装在可旋转的有效载荷支撑结构上。
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60.发明申请Method and Apparatus for Changing a Deployed Position for a Tail Skid Assembly 有权用于改变尾部滑动组件的部署位置的方法和装置公开(公告)号：US20130233970A1
公开(公告)日：2013-09-12
申请号：US13416914
申请日：2012-03-09
申请人： Justin Duane Cottet
发明人： Justin Duane Cottet
CPC分类号： B64C25/32 , B64C25/52 , B64C25/58 , B64C2025/005
摘要： A method and apparatus for positioning a tail skid assembly for a maximum rotation angle for an aircraft may be provided. A determination may be made as to whether the tail skid assembly is to be deployed for takeoff or landing. A set of parameters may be identified based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing. A desired maximum rotation angle for the aircraft may be identified using the set of parameters. The tail skid assembly may be deployed to allow the desired maximum rotation angle for the aircraft.
摘要翻译： 可以提供一种用于定位用于飞行器的最大旋转角度的尾部滑行组件的方法和装置。 可以确定尾部滑行组件是否要用于起飞或着陆。 可以基于是否将部署用于起飞或着陆的尾部滑行组件的确定来识别一组参数。 可以使用该组参数来识别用于飞行器的期望的最大旋转角度。 尾部滑行组件可以被部署以允许飞机的期望的最大旋转角度。
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